Flying-machine.



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a. CHMIELINSKI.

FLY'IKG MACHINE. APPL IcATIoN FIITEDDEC-HKJ'QII Patented Aug. 20, 191

4 SHEETS-SHEET 2.

a. CHMIELINS'KI'.

FLYING meme.

APPLICATION FILED DEC-14 1911.

Patenfei Aug. 20, 1912 hemispherical bow or nose' l and a done GREGORYCHMIELINSKI, OF CHICAGO, ILLINOIS.

FLYING-MACHINE.

Specification of Letters Patent.

Patented Aug. 20, 1918.

Application filed December 14, 1917. Serial No. 207,151.

To all whom it may concern:

Be it known that I, GREGORY Cl-IMI-ELI1*{ sin, a citizen ofPoland,'residing at Ch1 ca '0, in the county of Cook and State ofIllinois, have invented new and useful Iniprovements in Flying-Machines,of which the following is a specification.

,This invention relates to flying machines of the heavier than air type,the broad object in view being to produce alflylng machine of greatpassenger and freight carrying capacity and which may be also used intimes of war for transporting troops, ammunitions of war, and-also as abomb dropping machine.

The invention relates more particularly to the frame structure andgeneral arrangement of the fuselage or cabane and the aerial supportinand propelling means,

--whereby the mac ine may be handled with compariftive ease and wherebyincreased lifting properties are imparted to themachine, rendering thesame comparatively safe in operation, while at the same time impartingan unusual degree of stabillty both in a fore and aft and lateraldirection.

With the above and other objects in view the invention consists in thenovel construction, combination and arrangement of parts, as hereindescribed, illustrated and claimed.

In the accompanying drawings,

Figure 1 is a plan view of the improved flying machine.

Fig. 2 is a plan view partly in section of the frame of the fuselage orcaban'e.

Fig. 3 is a fragmentary perspective view of one of the end portions ofthe frame of the fuselage.

Fig. 4 is a fra entaryvertical section on an enlarged sca e through oneside of the fuselage.

Fig. 5 is a side elevation of the machine.

Fi 6 is a vertical transverse section on the line a-a of Fig. 5.

Fig. 7 is a front elevation of the machine.

Fig. 8 is a perspective view of one of the propellers.

Fig. 9 is a bottom lan view of the same.

Referring primari y to Fig. 1, the machine in its general arran ementand structure comprises front an rear lifting or gliding surfaces 1 and2, which are super imposed above a fore and aft elon ated fuselage orcabane 3 having a su stantially spondingly shaped stern 5, imparting tothe fuselage a stream-line formation which may be propelled through theair with a minimum head resistance.

Referring now-to Figs. 2, 6 and 7, the fuselage comprises a series ofcircular bands or hoops 6 constituting transverse members of the frame.All of the hoops or circular frame members 6 which are in the form ofendless rings, are connected at suitable intervals by means oflongitudinal tie bars or stringers 7 thus forming a reticulated hollowcylindrical frame for the fuselage. At the top and bottom of the framemembers 6, there are other longitudinal frame members or stringers 8, 9,10 and 11. The last named frame members are longer than the members 7previously referred to and are also secured fixedly to the ring likeframe members 6. The members 8, 9, 10 and 11, however, extend beyond thefront'and rear members 6 where they are each bent into the form of aquarter circle. The member 11 has a bifurcated extremity 12'whichstraddles the adjacent extremity '9. The member 8 has a bifurcated end13 which straddles the bifurcated end 12 of the member 11. The member 10has a bifurcated end 14: which straddles the bifurcated end 13 of themember 8. A single fastener 15 which mayconsist of a bolt, is insertedthrou h the interiitting ex tremities of said mem ers 8', 9, 10 and 11as shown in Fig. 3, the extremities of all of said members being thusfirmly secured together at the extreme bow and stern of the fuselage.A-covering 16 of any suitable ma terial, either metal or fabric is usedas a sheathing for the fuselage frame. At/the bow quadrant shaped glazedport holes or' windows 17 are provided. for the use'of the aviator aswell as other occupants of the machine.

As indicated in Fig. 1, I employ four separate and independent motors 18and four separate and independent propellers 19. Each propeller ismounted upon an individual propeller shaft 20 having fast thereon asprocket wheel 21 around which;

passes a chain 22 which extends around a sprocket wheel 23 on the shaftof the respective motor 18. Each shaft 20 is journaled in bearings 24:at; the lower extremities of' an equal numbed?" of hangers 25, which areconnected at th r upper ends to fittings 26 on the under si e of the adjacen't supporting or gliding surf co l-or 2 as the case may be.

ill-aces or sprmdcrs 27 extend from the fuselag lalcraltv outward andhavingtheir outer (Xlil'liiliiltfi fastened lo the bearings 2-}. Stays28 have their outer cxllclnilics coin'nw'twl to the bearings 24 and thefittings 225i and baniln-iiinner extremities fast ned ing the rain ofspeed of the several l'notors,

. speed of the 'n'opellcrs may be obtained to assist in steering andbanking operations and also for restoring and i'naintaining lat oral andion 'tudinal stability. The aviascat 30 is arranged cci'itmlly of theshown in l ig. ii, and llCljllCGlll to desi i'ial'ccl generally at El1.. By in m'n'isli'iwtion licro'iimborc out a sin o companioi'iway W is'lormod length of tln-v fuselage as 'l and. (i and pa" nger ang-od atopposite sides may or sin c aisle.

the proprg-llcrs is preferably of a sulistantially rectangular platelight metal such 2 aluminum or alunnuni alloy. Onftlie ui' ler side ofthe plate cleats 36 arranged substantially parallel and in. spacedrelation to each other are fastened to said sheet by means of rivets ordie equivalent thereof. About centrally of their length, the. cleats 36are formed with eyes 37 through which the respective pro- ?peller shaft20 is insert-ed and fastened. By r=ference to Figs. '7 and 8, it will beobserved that the end portions of the propeller are pitched or inclinedat a suitable angle to propel the machine ahead and at the same time 'tlifting propellers. Each of the s oiling or gliding surfaces 1 and 2 has.1d or wing portions upi-vardly inclined at and 7, while the extreme endportions there of are slightly rccurved in compound formation as shownin the same figures, giving a bird-like contour to said supporting andgliding surfaces.

In conjunction with each of the motors 18, I employ two fuel tanks 38and 39: Said tanks are arranged in the front and rear portions of thefuselage and leading from each pair of tanks to the respective motor 18are one'or more fuel feed pipes 40. At

the, stern of the fuselage, I arrange a rudder bracket 41 having a.semicircular base-.portion which is terminally fastened tothe fuse;-lagie at the points bracket 41 is bodying twotending arms rearwardlyextending arms 44.. A. centrally upwardly and rearwardly excreased bythe employment of the a dihedral angle as indicated in Figs. 15V

43 and two horizontally and comprising a fore and aft pivoted orbifurcated horizontal rudder 4-5 is mounted upon an operating rock shaft46 journalcd in the horizontal. arms 4% of the rudder bracket, and avertical rudder 47 is fast to an operating rock shaft 8 journaled in thehorizontal arms -13 of said rudder bracket. Suitable rudder operatingconnections extend from said rock shafts inboard Where they areconnected to one of the controls 31 hereinabove referred to.

The landing gear comprises an axle 49 extending transversely under thefuselage and having mounted thereon supporting wheels 00. Theaxle 49 iscarried by the lower extremities of vertical plunger rods 51 which areslidable through openings in a bottom bracket 52 fastened to the bottomof the fuselage fralneas shown, for example, in Fig. 6. Encircling' eachof the plunger rods 51 is a coil compression spring 53 which acts as ashock absorber and cushions the load of the machine in relation to theaxle 49. It will be seen from F ig. 5 that front and rear axles 4.9 areprovided for the proper support of the machine on the ground. Flexiblestays 54 may be interposed between each axle l9 and the bottom frame 52or the frame of the fuselage as may be preferred.

The construction hereinabove described provides for i a light weight,thoroughly braced fuselage and wing structure, the fuselage having alarge carrying ca acity for passengers or freight. By emp oying thefront and rear supporting or gliding sur' faces, the longitudinalstability of the machine is greatly increased as compared with thepresent date type of aeroplane which has the supporting and glidingsurface'or surfaces arranged adjacent to the head or how of thefuselage. Both the lateral and longitudinal stability of the machine arealso inpropellers under the arrangement described and shown. Ampleclearance for said propellers is pro vided at opposite sides of thefuselage and beneath the supporting and gliding surface. The bearingsfor the propeller shafts and the outriggers or. hangers therefor, are

will also be found a very desirable feature in case of in my to eitherthehorizontalor 42. At the rear end, sald of cruciform format-ion, em-'vertical rud adds greatly I-claim';

1. In a flying machine,

er or the controls thereof. to the safety .of the machine.

a fpselage frames e1 1e s of circularhoops, longitudinal frame bars towhich all of said hoops, are fastened, and other longitudinal frame barsto which said hoops are fastened, the last named frame bars extendingbeyond the front and rear hoops and having front end portions curvedinwardly and fastened at their extremities to provide hemispherical bowand stern portions for said fuselage frame.

In a flying machine, a fuselage frame comprising a fore and aft seriesof circular hoops, longitudinal frame bars to which all of said hoopsare fastened, and other longitudinal frame bars to which said hoops arefastened, the last named frame bars ex tending beyond the front and rearhoope end having front end portions curved in \i'nri'lly and fastened attheir extremities 0 provide hemisl'iherieal how and stern per tions forsaid fuselage frame, propeller shafts extending parallel to thelongitudinal axis of the fuselage frame, and supporting Outriggers forsaid shafts fastened to the fuselage frame.

3. In a flying machine, a fuselage frame comprising a fore and aftseries of circular hoops, longitudinal frmne here to which all of saidhoops are fastened, other longitudinail frame bars to which said hoopsare fastened, the lust named frame here extending beyond the front andrear hoops and having front end portions curved inwardly and festened attheir extremities to provide hemispheric-n1 bow and stern portions forsaid fuselage frame, the said curved end portions of the last named lon'itudinzrl frame bars being overlapped in bifurcated forms;- tion, andusingle fastener inserted through said overlapping extremities.

in testimony whereof I nflix my signature.

C: it l*l(l-( W Y ()H MIELIN SKI.

